Similarly shaped airfoils to NACA67A309
New! Bulk download of polars in Excel format: NACA67A309.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. NACA67-309 a=0.6
3. NACA66A309
4. NACA66-309 a=0.8
5. NACA67-309 a=0.5
6. NACA66-309 a=0.6
7. NACA66-409
8. NACA66-309
9. DP2.00/8.55_DS
10. NACA66A310
11. NACA66-310 a=0.8
12. NACA66-309 a=0.5
13. NACA65A309
14. NACA67A310
15. NACA67-310 a=0.8
16. NACA66-410
17. NACA66-310 a=0.6
18. DP1.79/8.37_DS
19. NACA65A310
20. NACA67-309 a=0.2
21. NACA67-310 a=0.6